Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

WORTMANN FX 80-080 (fx80080-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 80-080 (fx80080-il)
Reynolds number: 1,000,000
Max Cl/Cd: 123.6 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx80080-il-1000000.txt
Download as CSV file: xf-fx80080-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 80-080                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3472   0.08284   0.08132  -0.0343   1.0000   0.0082
  -9.250  -0.3496   0.07846   0.07696  -0.0351   1.0000   0.0083
  -9.000  -0.3513   0.07447   0.07299  -0.0358   1.0000   0.0083
  -8.750  -0.3550   0.07014   0.06867  -0.0366   1.0000   0.0083
  -6.250  -0.3236   0.02048   0.01697  -0.0847   0.9508   0.0085
  -6.000  -0.2880   0.01849   0.01467  -0.0872   0.9432   0.0084
  -5.750  -0.2554   0.01416   0.00971  -0.0895   0.9351   0.0087
  -5.500  -0.2242   0.01203   0.00727  -0.0908   0.9263   0.0092
  -5.250  -0.1945   0.01099   0.00608  -0.0914   0.9177   0.0098
  -5.000  -0.1645   0.01046   0.00545  -0.0921   0.9101   0.0108
  -4.750  -0.1382   0.00985   0.00474  -0.0919   0.9023   0.0116
  -4.250  -0.0849   0.00898   0.00367  -0.0915   0.8893   0.0129
  -4.000  -0.0586   0.00851   0.00310  -0.0913   0.8835   0.0138
  -3.750  -0.0339   0.00789   0.00237  -0.0907   0.8779   0.0168
  -3.500  -0.0074   0.00768   0.00211  -0.0905   0.8726   0.0195
  -3.250   0.0199   0.00744   0.00177  -0.0904   0.8680   0.0241
  -3.000   0.0456   0.00718   0.00157  -0.0900   0.8631   0.0399
  -2.750   0.0720   0.00698   0.00143  -0.0898   0.8585   0.0634
  -2.500   0.0990   0.00678   0.00132  -0.0898   0.8543   0.1019
  -2.250   0.1241   0.00644   0.00122  -0.0895   0.8500   0.1775
  -2.000   0.1473   0.00578   0.00110  -0.0890   0.8455   0.3560
  -1.750   0.1691   0.00500   0.00102  -0.0883   0.8414   0.5936
  -1.500   0.1935   0.00477   0.00106  -0.0876   0.8374   0.6980
  -1.250   0.2201   0.00473   0.00107  -0.0872   0.8332   0.7281
  -1.000   0.2470   0.00473   0.00107  -0.0870   0.8290   0.7481
  -0.750   0.2740   0.00475   0.00110  -0.0867   0.8245   0.7688
  -0.500   0.3003   0.00474   0.00111  -0.0863   0.8188   0.7815
  -0.250   0.3272   0.00477   0.00112  -0.0860   0.8131   0.7949
   0.000   0.3531   0.00477   0.00115  -0.0855   0.8069   0.8083
   0.250   0.3793   0.00479   0.00117  -0.0851   0.8005   0.8201
   0.500   0.4053   0.00480   0.00119  -0.0846   0.7932   0.8306
   0.750   0.4314   0.00484   0.00120  -0.0841   0.7850   0.8396
   1.000   0.4572   0.00481   0.00121  -0.0836   0.7759   0.8461
   1.250   0.4834   0.00483   0.00122  -0.0831   0.7657   0.8516
   1.500   0.5096   0.00485   0.00122  -0.0828   0.7559   0.8565
   1.750   0.5353   0.00486   0.00123  -0.0822   0.7433   0.8614
   2.000   0.5614   0.00490   0.00126  -0.0818   0.7306   0.8665
   2.250   0.5865   0.00494   0.00130  -0.0812   0.7104   0.8713
   2.500   0.6111   0.00502   0.00134  -0.0804   0.6874   0.8767
   2.750   0.6353   0.00514   0.00139  -0.0796   0.6577   0.8826
   3.000   0.6561   0.00539   0.00148  -0.0781   0.6011   0.8892
   3.250   0.6726   0.00598   0.00169  -0.0758   0.5021   0.8976
   3.500   0.6863   0.00682   0.00203  -0.0732   0.3724   0.9077
   3.750   0.7015   0.00760   0.00235  -0.0709   0.2566   0.9202
   4.000   0.7202   0.00815   0.00263  -0.0693   0.1797   0.9380
   4.250   0.7493   0.00864   0.00292  -0.0700   0.1236   0.9670
   4.500   0.7786   0.00908   0.00321  -0.0707   0.0871   1.0000
   4.750   0.8024   0.00945   0.00349  -0.0701   0.0653   1.0000
   5.000   0.8265   0.00979   0.00377  -0.0696   0.0500   1.0000
   5.250   0.8501   0.01017   0.00407  -0.0689   0.0362   1.0000
   5.500   0.8735   0.01056   0.00441  -0.0682   0.0258   1.0000
   5.750   0.8965   0.01100   0.00486  -0.0673   0.0199   1.0000
   6.000   0.9206   0.01132   0.00519  -0.0668   0.0170   1.0000
   6.250   0.9416   0.01197   0.00590  -0.0655   0.0133   1.0000
   6.500   0.9660   0.01224   0.00619  -0.0650   0.0122   1.0000
   6.750   0.9896   0.01259   0.00654  -0.0644   0.0101   1.0000
   7.000   1.0065   0.01372   0.00780  -0.0623   0.0079   1.0000
   7.250   1.0300   0.01407   0.00819  -0.0617   0.0073   1.0000
   7.500   1.0525   0.01455   0.00870  -0.0608   0.0062   1.0000
   7.750   1.0740   0.01513   0.00935  -0.0598   0.0056   1.0000
   8.000   1.0904   0.01635   0.01068  -0.0579   0.0049   1.0000
   8.250   1.1061   0.01780   0.01230  -0.0559   0.0046   1.0000
   8.500   1.1250   0.01882   0.01345  -0.0545   0.0045   1.0000
   8.750   1.1441   0.01984   0.01460  -0.0532   0.0044   1.0000
   9.000   1.1623   0.02098   0.01589  -0.0517   0.0042   1.0000
   9.250   1.1794   0.02228   0.01735  -0.0502   0.0041   1.0000
   9.500   1.1948   0.02386   0.01912  -0.0484   0.0040   1.0000
   9.750   1.2095   0.02533   0.02078  -0.0466   0.0038   1.0000
  10.000   1.2266   0.02601   0.02157  -0.0452   0.0035   1.0000
  10.250   1.2319   0.02879   0.02467  -0.0421   0.0035   1.0000
  10.500   1.2399   0.03050   0.02658  -0.0395   0.0034   1.0000
  10.750   1.2532   0.03064   0.02674  -0.0375   0.0031   1.0000
  11.000   1.2545   0.03234   0.02861  -0.0340   0.0031   1.0000
  11.250   1.2511   0.03445   0.03095  -0.0301   0.0030   1.0000
  11.500   1.2453   0.03634   0.03296  -0.0264   0.0028   1.0000
  11.750   1.2347   0.03909   0.03595  -0.0228   0.0028   1.0000
  12.000   1.2225   0.04210   0.03918  -0.0198   0.0028   1.0000
  12.250   1.1941   0.04698   0.04435  -0.0168   0.0027   1.0000
  12.500   1.1781   0.05092   0.04848  -0.0155   0.0027   1.0000
  12.750   1.1671   0.05465   0.05237  -0.0151   0.0028   1.0000
  13.000   1.1428   0.06053   0.05845  -0.0160   0.0028   1.0000
  13.250   1.1128   0.06856   0.06672  -0.0190   0.0029   1.0000
  13.500   1.0990   0.07480   0.07304  -0.0229   0.0028   1.0000
  13.750   1.0741   0.08578   0.08418  -0.0306   0.0028   1.0000
<< Back to WORTMANN FX 80-080 (fx80080-il)

Polar data table (+)

Polar graphs


<< Back to WORTMANN FX 80-080 (fx80080-il)